EP1655475B1 - Counter-rotating turbine engine - Google Patents
Counter-rotating turbine engine Download PDFInfo
- Publication number
- EP1655475B1 EP1655475B1 EP05255228A EP05255228A EP1655475B1 EP 1655475 B1 EP1655475 B1 EP 1655475B1 EP 05255228 A EP05255228 A EP 05255228A EP 05255228 A EP05255228 A EP 05255228A EP 1655475 B1 EP1655475 B1 EP 1655475B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- pressure turbine
- rotor
- low
- foil
- foil bearing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/02—Sliding-contact bearings for exclusively rotary movement for radial load only
- F16C17/024—Sliding-contact bearings for exclusively rotary movement for radial load only with flexible leaves to create hydrodynamic wedge, e.g. radial foil bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/12—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load
- F16C17/18—Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with floating brasses or brushing, rotatable at a reduced speed
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
- F05D2240/53—Hydrodynamic or hydrostatic bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
Definitions
- This invention relates generally to aircraft gas turbine engines, and more specifically to counter-rotating gas turbine engines.
- At least one known gas turbine engine includes, in serial flow arrangement, a forward fan assembly, an aft fan assembly, a high-pressure compressor for compressing air flowing through the engine, a combustor for mixing fuel with the compressed air such that the mixture may be ignited, and a high-pressure turbine.
- the high-pressure compressor, combustor and high-pressure turbine are sometimes collectively referred to as the core engine.
- the core engine generates combustion gases which are discharged downstream to a counter-rotating low-pressure turbine that extracts energy therefrom for powering the forward and aft fan assemblies.
- at least one turbine rotates in an opposite direction than the other rotating components within the engine
- At least one known counter-rotating low-pressure turbine has an inlet radius that is larger than a radius of the high-pressure turbine discharge. The increased size of the inlet radius accommodates additional stages within the low-pressure turbine.
- at least one known counter-rotating low-pressure turbine includes an outer turbine having a first quantity of low-pressure stages that are rotatably coupled to the forward fan assembly, and an inner turbine having an equal number of stages that is rotatably coupled to the aft fan assembly.
- such known gas turbine engines are assembled such that the outer turbine is cantilevered from the turbine rear frame. More specifically, the first quantity of stages of the outer turbine are each coupled together and to the rotating casing, and the outer turbine is then coupled to the turbine rear frame using only the last stage of the outer turbine, such that only the last stage of the outer turbine supports the combined weight of the outer turbine rotating casing. Accordingly, to provide the necessary structural strength to such engines, the last stage of the outer turbine is generally much larger and heavier than the other stages of the outer turbine. As such, during operation, the performance penalties associated with the increased weight and size may actually negate the benefits of utilizing a counter-rotating low-pressure turbine.
- EP 1 403 485 describes a gas turbine engine with a low pressure turbine comprising counter rotatable low pressure inner and outer shaft turbines.
- Gas turbine engine 10 also includes a core engine 24 that is downstream from fan assemblies 12 and 14.
- Core engine 24 includes a high-pressure compressor (HPC) 26, a combustor 28, and a high-pressure turbine (HPT) 30 that is coupled to HPC 26 via a core rotor or shaft 32.
- HPC high-pressure compressor
- HPT high-pressure turbine
- core engine 24 generates combustion gases that are channeled downstream to a counter-rotating low-pressure turbine 34 which extracts energy from the gases for powering fan assemblies 12 and 14 through their respective fan shafts 20 and 22.
- Low-pressure turbine 34 also includes a radially inner rotor 42 that is aligned substantially coaxially with respect to, and radially inward of, outer rotor 38.
- Inner rotor 42 includes a plurality of circumferentially-spaced rotor blades 44 that extend radially outwardly and are arranged in axially-spaced rows or stages 43.
- the exemplary embodiment only illustrates five stages, it should be realized that inner rotor 42 may have any quantity of stages without affecting the scope of the method and apparatus described herein.
- a rotatable aft frame 51 is positioned aft of outer and inner blades 40 and 44 and upstream from rear frame 46.
- Frame 51 is coupled to an aft end of outer rotor 38 for rotation therewith and to facilitate providing additional rigidity for supporting blades 40.
- Aft frame 51 includes a plurality of circumferentially-spaced struts 52 that are coupled to radially outer and inner annular aft bands 53 and 54 such that inner aft band 54 is fixedly secured to an annular aft support shaft 55 for rotation therewith.
- Shaft 55 extends radially inward from, and upstream from, rear frame 46.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Support Of The Bearing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
- This invention relates generally to aircraft gas turbine engines, and more specifically to counter-rotating gas turbine engines.
- At least one known gas turbine engine includes, in serial flow arrangement, a forward fan assembly, an aft fan assembly, a high-pressure compressor for compressing air flowing through the engine, a combustor for mixing fuel with the compressed air such that the mixture may be ignited, and a high-pressure turbine. The high-pressure compressor, combustor and high-pressure turbine are sometimes collectively referred to as the core engine. In operation, the core engine generates combustion gases which are discharged downstream to a counter-rotating low-pressure turbine that extracts energy therefrom for powering the forward and aft fan assemblies. Within at least some known gas turbine engines, at least one turbine rotates in an opposite direction than the other rotating components within the engine
- At least one known counter-rotating low-pressure turbine has an inlet radius that is larger than a radius of the high-pressure turbine discharge. The increased size of the inlet radius accommodates additional stages within the low-pressure turbine. Specifically, at least one known counter-rotating low-pressure turbine includes an outer turbine having a first quantity of low-pressure stages that are rotatably coupled to the forward fan assembly, and an inner turbine having an equal number of stages that is rotatably coupled to the aft fan assembly.
- During engine assembly, such known gas turbine engines are assembled such that the outer turbine is cantilevered from the turbine rear frame. More specifically, the first quantity of stages of the outer turbine are each coupled together and to the rotating casing, and the outer turbine is then coupled to the turbine rear frame using only the last stage of the outer turbine, such that only the last stage of the outer turbine supports the combined weight of the outer turbine rotating casing. Accordingly, to provide the necessary structural strength to such engines, the last stage of the outer turbine is generally much larger and heavier than the other stages of the outer turbine. As such, during operation, the performance penalties associated with the increased weight and size may actually negate the benefits of utilizing a counter-rotating low-pressure turbine.
-
US 6,725,643 describes high efficiency gas turbine power generator systems. -
EP 1 403 485 describes a gas turbine engine with a low pressure turbine comprising counter rotatable low pressure inner and outer shaft turbines. - Various aspects and embodiments of the present invention are defined in the appended claims.
- Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which:
- Figure 1 is a cross-sectional view of a portion of an exemplary gas turbine engine;
- Figure 2 is a cross-sectional view of a portion of an exemplary counter-rotating low-pressure turbine;
- Figure 3 is an enlarged view of an aft portion of counter-rotating low-pressure turbine including the exemplary foil bearing shown in Figure 2;
- Figure 4 is a side view of
foil bearing assembly 100 taken along view B-B; - Figure 5 is an side view of an exemplary foil bearing;
- Figure 6 is a cross-sectional view of a portion of counter-rotating low-pressure turbine that includes an exemplary foil bearing;
- Figure 7 is an expanded view of a forward portion of counter-rotating low-pressure turbine including the exemplary foil bearing shown in Figure 6;
- Figure 8 is an expanded view of an aft portion of counter-rotating low-pressure turbine including the exemplary foil bearing shown in Figure 6;
- Figure 9 is a cross-sectional view of a portion of counter-rotating low-pressure turbine that includes an exemplary foil bearing;
- Figure 10 is an end view of the foil bearing shown in Figure 9;
- Figure 11 is a schematic illustration of a gas turbine engine including an exemplary foil bearing; and
- Figure 12 illustrates a portion of a gas turbine engine including the exemplary foil bearing shown in Figure 11.
- Figure 1 is a cross-sectional view of a portion of an exemplary
gas turbine engine 10 that includes aforward fan assembly 12 and anaft fan assembly 14 disposed about alongitudinal centerline axis 16. The terms "forward fan" and "aft fan" are used herein to indicate that one of thefans 12 is coupled axially upstream from theother fan 14. In one embodiment,fan assemblies gas turbine engine 10 as illustrated. In an alternative embodiment,fan assemblies gas turbine engine 10. Fan assemblies 12 and 14 each include a plurality of rows offan blades 19 positioned within anacelle 18.Blades 19 are joined torespective rotor disks 21 that are rotatably coupled through arespective fan shaft 20 toforward fan assembly 12 and through afan shaft 22 toaft fan assembly 14. -
Gas turbine engine 10 also includes acore engine 24 that is downstream fromfan assemblies Core engine 24 includes a high-pressure compressor (HPC) 26, acombustor 28, and a high-pressure turbine (HPT) 30 that is coupled to HPC 26 via a core rotor orshaft 32. In operation,core engine 24 generates combustion gases that are channeled downstream to a counter-rotating low-pressure turbine 34 which extracts energy from the gases for powering fan assemblies 12 and 14 through theirrespective fan shafts - Figure 2 is a cross-sectional view of a portion of counter-rotating low-
pressure turbine 34. In the exemplary embodiment, low-pressure turbine 34 includes a stationaryouter casing 36 that is coupled tocore engine 24 downstream from high-pressure turbine 30 (shown in Figure 1). Low-pressure turbine 34 includes a radiallyouter rotor 38 that is positioned radially inwardly ofouter casing 36.Outer rotor 38 has a generally frusto-conical shape and includes a plurality of circumferentially-spacedrotor blades 40 that extend radially inwardly.Blades 40 are arranged in axially-spaced blade rows orstages 41. Although, the exemplary embodiment only illustrates fourstages 41, it should be realized thatouter rotor 38 may have any quantity ofstages 41 without affecting the scope of the method and apparatus described herein. - Low-
pressure turbine 34 also includes a radiallyinner rotor 42 that is aligned substantially coaxially with respect to, and radially inward of,outer rotor 38.Inner rotor 42 includes a plurality of circumferentially-spacedrotor blades 44 that extend radially outwardly and are arranged in axially-spaced rows orstages 43. Although, the exemplary embodiment only illustrates five stages, it should be realized thatinner rotor 42 may have any quantity of stages without affecting the scope of the method and apparatus described herein. - In the exemplary embodiment,
inner rotor blades 44 extending fromstages 43 are axially-interdigitated withouter rotor blades 40 extending fromstages 41 such thatinner rotor stages 43 extend between respectiveouter rotor stages 41. Theblades rotors - In the exemplary embodiment, low-
pressure turbine 34 also includes arotor support assembly 45 that includes a stationary annularrear frame 46 that is aft of low-pressure turbine outer andinner blades Rear frame 46 includes a plurality of circumferentially-spacedstruts 47 that are coupled at their outer ends to an annularouter band 48 that is coupled toouter casing 36, and coupled at their inner ends to an annular inner band orhub 49.Rear frame 46 also includes an annularnon-structural flowpath extension 50 that extends radially inward. In the exemplary embodiment,rear struts 47 are positioned in flow communication with an aft end of low-pressure turbine 34 for receiving the combustion gases therefrom. - A
rotatable aft frame 51 is positioned aft of outer andinner blades rear frame 46.Frame 51 is coupled to an aft end ofouter rotor 38 for rotation therewith and to facilitate providing additional rigidity for supportingblades 40.Aft frame 51 includes a plurality of circumferentially-spacedstruts 52 that are coupled to radially outer and innerannular aft bands inner aft band 54 is fixedly secured to an annularaft support shaft 55 for rotation therewith. Shaft 55 extends radially inward from, and upstream from,rear frame 46. Outer andinner bands struts 52 together to form a relatively rigid assembly. Accordingly, the combination of circumferentially-spacedstruts 52 and outer andinner bands outer rotor 38 toouter casing 36 through an aft foil bearing 100. Foil bearing 100 may eliminate the need to transfer loads fromouter rotor 38 torear frame 46 through an additional aft bearing/housing structure (not shown). - An
annular mid-frame 60 is upstream from outer andinner blades forward struts 62 that are coupled to a radiallyouter front band 64 and to a radiallyinner front band 66. Innerfront band 66 is also coupled to anannular shaft 68 that extends radially inward fromband 66. In the exemplary embodiment,turbine mid-frame 60 is fixedly secured toouter casing 36 viaouter front band 64. In the exemplary embodiment,forward struts 62 are enclosed by afairing 70 that facilitatesshielding struts 62 from hot combustion gases flowing throughengine 10. In another embodiment,struts 62 are not enclosed by fairing 70. - In the exemplary embodiment,
gas turbine engine 10 includes a plurality offoil bearings 100 that are positioned betweenouter rotor 38 andcasing 36. In one embodiment, a first quantity ofbearings 102 are positioned at anaft end 104 of low-pressure turbine 34, and a second quantity ofbearings 106 are positioned at aforward end 108 of low-pressure turbine 34.Foil bearings 100 facilitate providing structural support to low-pressure turbine 34 during maneuver loading. More specifically, foilbearings 100 are circumferentially spaced about anexterior surface 110 ofouter rotor 38 to facilitate providing rotational support to low-pressure turbine 34. More specifically, and in the exemplary embodiment, four foil bearings are circumferentially spaced approximately equidistantly about an outer periphery of low-pressure turbine 34 ataft end 104, and four foil bearings are circumferentially spaced approximately equidistantly about an outer periphery of low-pressure turbine 34 atforward end 108. Accordingly, in the exemplary embodiment, a weight of low-pressure turbine 34 is distributed approximately equally about the circumference ofgas turbine engine 10 at both forward and aft ends 108 and 104 respectively. - Figure 3 is an enlarged view of an aft portion of counter-rotating low-
pressure turbine 34 includingfoil bearing assembly 100. Figure 4 is a side view offoil bearing assembly 100 taken along view B-B. Figure 5 is an side view of anexemplary foil bearing 101. In the exemplary embodiment,foil bearing assembly 100 includes asupport member 122 that is fixedly secured to casing 36 using a plurality offasteners 124 and is rotatably coupled to foilbearing 101 using at least onefastener 126. - In the exemplary embodiment, foil bearing 101 includes a paired
race 130, and at least onefoil element 132. Pairedrace 130 includes anouter race 134 and aninner race 136 that is radially inward fromouter race 134.Foil elements 132 extend betweeninner race 136 andouter race 134 and each include a plurality of compliant metal foils 132 that are each secured toouter race 134 to facilitateinner race 136 rotating relative toouter race 134, or, as in this embodiment,outer race 134 rotating relative toinner race 136. In the exemplary embodiment, foilbearings 101 facilitate reducing the affects of maneuver loads on counter-rotating low-pressure turbine 34 while also increasing clearance control and sealing between the rotors. Further, using foil bearings withingas turbine engine 10 facilitates reducing a fabrication cost of the gas turbine engine since the foil bearings do not require lubrication, have no DN speed limit, wherein D is defined as a diameter of the bearing bore in millimeters, and N is defined as the top speed of the bearing in revolutions per minute, require no maintenance, and are self-acting hydrodynamic "float on air" devices. - In the exemplary embodiment, during engine operation, a radial force generated during rotation of low-
pressure turbine 34 is transmitted to foilbearings 101. More, specifically, as low-pressure turbine 34 rotates, anexterior surface 138 of foil bearing 101 contacts anexterior surface 139 of low-pressure turbine 34 to facilitate reducing radial movement of low-pressure turbine 34. Since each respective foil bearing 101 is coupled toouter casing 36 throughsupport member 122, low-pressure turbine 34 maintains a relatively constant radial position with respect toouter casing 36. More specifically, as low-pressure turbine 34 is forced radially outward during operation, because foil bearing 101 is attached toouter casing 36, any radial movement of low-pressure turbine 34 is transmitted to casing 36 such that low-pressure turbine 34 is maintained in a relatively constant radial position with respect toouter casing 36. - Figure 6 is a cross-sectional view of a portion of counter-rotating low-
pressure turbine 34 including an exemplaryfoil bearing assembly 200. Figure 7 is an enlarged view of a forward portion of counter-rotating low-pressure turbine 34 includingfoil bearing assembly 200. Figure 8 is an enlarged view of an aft portion of counter-rotating low-pressure turbine 34 includingfoil bearing assembly 200. - In the exemplary embodiment, low-
pressure turbine 34 includes a firstfoil bearing assembly 202 low-pressure turbine aftend 104.Bearing assembly 202 includes afoil bearing 204 and asupport member 206 that is fixedly secured to casing 36 using a plurality offasteners 208.Support member 206 is rotatably coupled about an outer periphery of radiallyouter rotor 38 such that foil bearing 204 circumscribes radiallyouter rotor 38. - In another exemplary embodiment,
gas turbine engine 10 includes a secondfoil bearing assembly 210 that is positioned at low-pressure turbineforward end 108. In the exemplary embodiment, bearingassembly 210 includes afoil bearing 212 and asupport member 214 that is fixedly secured to casing 36 using a plurality offasteners 216 and is rotatably coupled about an outer periphery of radiallyouter rotor 38 such that foil bearing 212 circumscribes radiallyouter rotor 38. - In the exemplary embodiment, foil
bearings race 230 and at least onefoil element 232. Pairedrace 230 includes anouter race 234 and aninner race 236 that is radially inward fromouter race 234.Foil elements 232 extend betweeninner race 236 andouter race 234. Specifically, foilbearings inner race 236 and/orouter race 234 to facilitateinner race 236 rotating relative toouter race 234. In another embodiment, foilbearings inner race 236, but rather each includes a plurality of compliant metal foils 232 that are coupled toouter race 234 are frictionally coupled tocasing 36. In the exemplary embodiment, foilbearings pressure turbine 34 while also increasing clearance control and sealing between the rotors. Further, using foil bearings withingas turbine engine 10 facilitates reducing a fabrication cost of the gas turbine engine since the foil bearings do not require lubrication, have no DN speed limit, require no maintenance, and are self-acting hydrodynamic "float on air" devices. - In the exemplary embodiment, during engine operation, a radial force generated during rotation of low-
pressure turbine 34 is transmitted to foilbearings pressure turbine 34 rotates, anexterior surface 240 offoil bearings exterior surface 244 of low-pressure turbine 34 to facilitate reducing radial movement of low-pressure turbine 34. Since each respective foil bearing 204 and 212 is coupled toouter casing 36 throughsupport member 206, low-pressure turbine 34 is maintained in a relatively constant radial position with respect toouter casing 36. More specifically, as low-pressure turbine 34 is forced radially outward during operation, becausefoil bearings outer casing 36 such that at least one of theinner race 236 and/or metal foils 232 circumscribe an exterior surface of low-pressure turbine 34, any radial movement of low-pressure turbine 34 is transmitted to casing 36 such that low-pressure turbine 34 is maintained in a relatively constant radial position with respect toouter casing 36. - Figure 9 is a cross-sectional view of a portion of counter-rotating low-
pressure turbine 34 including anexemplary foil bearing 300. Figure 10 is an end view offoil bearing 300. In the exemplary embodiment, foil bearing 300 is a differential foil bearing that extends betweenshafts foil pack 310, acenter race 312, and a second or inward facingfoil pack 314. During operation, foil bearing 300 facilitates reducing shaft deflections betweenshafts gas turbine engine 10 is operating during maneuvering loads. - In the exemplary embodiment, foil bearing 300 facilitates reducing the affects of maneuver loads on counter-rotating low-
pressure turbine 34 while also increasing clearance control and sealing between the rotors. Further, using foil bearings withingas turbine engine 10 facilitates reducing a fabrication cost of the gas turbine engine since the foil bearings do not require lubrication, have no DN speed limit, require no maintenance, and are self-acting hydrodynamic "float on air" devices. - Figure 11 is a schematic illustration of
gas turbine engine 10 including at least onefoil bearing 400. Figure 12 illustrates a portion ofgas turbine engine 10 includingfoil bearing 400. In one embodiment, high-pressure turbine 30 is coupled to a high-pressure turbine spool 410 which is coupled to a low-pressure turbine stage 1nozzle assembly 412 through asupport 414.Foil bearing 400 extends betweensupport 414 and high-pressure turbine spool 410. More specifically, foil bearing 400 has an inner diameter and/orwidth 420 that is selectively sized to enable foil bearing 400 to circumscribe and outer periphery of high-pressure turbine spool 410. Accordingly, bearing 400 facilitates providing support to high-pressure turbine 30. - In another embodiment, high-
pressure turbine 30 is coupled to a high-pressure turbine spool 410 which is rotatably coupled toturbine mid-frame 60 throughsupport 414.Foil bearing 400 extends betweensupport 414 and high-pressure turbine spool 410. More specifically, foil bearing 400 has an inner diameter and/orwidth 420 that is selectively sized such that foil bearing 400 circumscribes and outer periphery of high-pressure turbine spool 410 and thus facilitates providing support to high-pressure turbine 30. In a further embodiment, each respective roller bearing withingas turbine 10 is replaced with a foil bearing. - The above-described foil bearing systems provide a cost-effective and highly reliable method for improving clearance control of a counter-rotating low-pressure turbine rotor. Moreover, because of the size of the counter-rotating low-pressure turbine rotor, maneuver loads may affect the operation of the gas turbine engine. Accordingly, fabricating a gas turbine engine that includes foil bearings facilitates reducing the affects of maneuver loads on the counter-rotating low-pressure turbine while also increasing clearance control and sealing between the rotors. Further, using foil bearings within the gas turbine engine facilitates reducing a fabrication cost of the gas turbine engine since the foil bearings do not require lubrication, have no DN speed limit, wherein D is defined as a diameter of the bearing bore in millimeters, and N is defined as the top speed of the bearing in revolutions per minute, require no maintenance, and are self-acting hydrodynamic "float on air" devices.
- Additionally, foil bearings can be used to complement existing conventional oil bearings during maneuver loads and/or to eliminate the need for lube, scavenge, drain systems as well as sump pressurization and vent across the counter-rotating low-pressure turbine module. When foil bearings are utilized in a gas turbine engine having a counter-rotating turbine, both conventional and differential bearings are eliminated. The method and system described herein further facilitate enabling the support of the three rotor design with utilizing two main frames and eliminates the need for a conventional turbine rear frame thus optimizing rotor support under all conditions while reducing system weight, cost, and complexity.
- Exemplary embodiments of gas turbine systems are described above in detail. The gas turbine systems are not limited to the specific embodiments described herein, but rather, components of the systems may be utilized independently and separately from other components described herein. Each gas path component can also be used in combination with other gas path components.
Claims (6)
- A rotor assembly (45) comprising:an inner rotor (42) configured to rotate in a first rotational direction;an outer rotor (38) configured to rotate in a second rotational direction that is opposite the first rotational direction; andcharacterized by:a plurality of foil bearings (102) circumferentially spaced approximately equidistantly about an outer periphery of said outer rotor (38), configured to support at least one of said inner and outer rotors.
- A rotor assembly (45) in accordance with Claim 1 wherein said outer rotor (38) is coupled radially inward of an outer casing (36) and includes a plurality of axially-spaced rows (41) of outer blades (40), said outer blades extend radially inward from said outer casing, and said inner rotor (42) is coupled radially inward of said outer rotor and includes a plurality of axially-spaced rows (43) of inner blades (44), said inner blades extending radially inward such that said inner blades are axially interdigitated with said outer blades.
- A rotor assembly (45) in accordance with Claim 1 wherein said foil bearing (100) is coupled to said outer rotor (38) such that said foil bearing circumscribes said outer rotor.
- A rotor assembly (45) in accordance with Claim 1 further comprising:a first shaft (22) coupled to said inner rotor (42) and a first fan (14);a second shaft (20) coupled to said outer rotor (38) and a second fan (12); anda differential foil bearing (300) positioned between said first and second shafts.
- A gas turbine engine (10) comprising a rotor assembly (45) in accordance with claim 1.
- A gas turbine engine (10) in accordance with Claim 5 further comprising:a high-pressure turbine spool (410);at least one of a low-pressure turbine (34) stage one nozzle (412) and a turbine mid-frame (60); anda foil bearing (400) coupled between at least one of said low-pressure turbine stage one nozzle and said turbine mid-frame such that said foil bearing supports the high-pressure turbine (30).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/976,496 US7195446B2 (en) | 2004-10-29 | 2004-10-29 | Counter-rotating turbine engine and method of assembling same |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1655475A1 EP1655475A1 (en) | 2006-05-10 |
EP1655475B1 true EP1655475B1 (en) | 2007-12-12 |
Family
ID=35033621
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05255228A Expired - Fee Related EP1655475B1 (en) | 2004-10-29 | 2005-08-25 | Counter-rotating turbine engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US7195446B2 (en) |
EP (1) | EP1655475B1 (en) |
JP (1) | JP4693551B2 (en) |
CN (1) | CN1854486B (en) |
DE (1) | DE602005003759T2 (en) |
Families Citing this family (67)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7269938B2 (en) * | 2004-10-29 | 2007-09-18 | General Electric Company | Counter-rotating gas turbine engine and method of assembling same |
FR2908452A1 (en) * | 2006-11-15 | 2008-05-16 | Snecma Sa | Fastener device for a gas turbine engine has a flange that provides releasable connections by mutual engagement between turbine stator and a gas generator casing and a sliding joint that provides centering of turbine stator on the casing |
US8534074B2 (en) * | 2008-05-13 | 2013-09-17 | Rolls-Royce Corporation | Dual clutch arrangement and method |
US20140174056A1 (en) | 2008-06-02 | 2014-06-26 | United Technologies Corporation | Gas turbine engine with low stage count low pressure turbine |
US8128021B2 (en) | 2008-06-02 | 2012-03-06 | United Technologies Corporation | Engine mount system for a turbofan gas turbine engine |
US20100005810A1 (en) * | 2008-07-11 | 2010-01-14 | Rob Jarrell | Power transmission among shafts in a turbine engine |
US8480527B2 (en) * | 2008-08-27 | 2013-07-09 | Rolls-Royce Corporation | Gearing arrangement |
FR2938013B1 (en) * | 2008-11-04 | 2015-08-07 | Microturbo | TURBOMACHINE WITH MIXED TREE SUPPORT BEARINGS. |
US8011877B2 (en) * | 2008-11-24 | 2011-09-06 | General Electric Company | Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades |
US8021267B2 (en) * | 2008-12-11 | 2011-09-20 | Rolls-Royce Corporation | Coupling assembly |
US8075438B2 (en) * | 2008-12-11 | 2011-12-13 | Rolls-Royce Corporation | Apparatus and method for transmitting a rotary input into counter-rotating outputs |
CN101963073B (en) * | 2009-07-22 | 2012-05-23 | 中国科学院工程热物理研究所 | Counterrotating turbine with overhung rotor blade structure |
US8734085B2 (en) * | 2009-08-17 | 2014-05-27 | Pratt & Whitney Canada Corp. | Turbine section architecture for gas turbine engine |
FR2976024B1 (en) * | 2011-05-31 | 2015-10-30 | Snecma | GAS TURBINE ENGINE COMPRISING THREE ROTARY BODIES |
US9631558B2 (en) | 2012-01-03 | 2017-04-25 | United Technologies Corporation | Geared architecture for high speed and small volume fan drive turbine |
US9239012B2 (en) | 2011-06-08 | 2016-01-19 | United Technologies Corporation | Flexible support structure for a geared architecture gas turbine engine |
US8973373B2 (en) | 2011-10-31 | 2015-03-10 | General Electric Company | Active clearance control system and method for gas turbine |
US20130192256A1 (en) * | 2012-01-31 | 2013-08-01 | Gabriel L. Suciu | Geared turbofan engine with counter-rotating shafts |
US9028200B2 (en) * | 2012-02-29 | 2015-05-12 | United Technologies Corporation | Counter rotating low pressure turbine with splitter gear system |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US20150308351A1 (en) | 2012-05-31 | 2015-10-29 | United Technologies Corporation | Fundamental gear system architecture |
US8756908B2 (en) | 2012-05-31 | 2014-06-24 | United Technologies Corporation | Fundamental gear system architecture |
US8572943B1 (en) | 2012-05-31 | 2013-11-05 | United Technologies Corporation | Fundamental gear system architecture |
FR3005099B1 (en) * | 2013-04-30 | 2017-08-25 | Snecma | TURBOMACHINE STRUCTURE COMPRISING A VENTILATION RING |
US9410430B2 (en) | 2014-06-19 | 2016-08-09 | Jay HASKIN | Turbine apparatus with counter-rotating blades |
BE1022364B1 (en) * | 2014-10-27 | 2016-03-17 | Techspace Aero S.A. | AXIAL TURBOMACHINE COMPRESSOR WITH DOUBLE CONTRAROTATIVE ROTORS |
GB201512494D0 (en) * | 2015-07-17 | 2015-08-19 | Rolls Royce Plc And Rolls Royce Deutschland Ltd & Co Kg | Gas turbine engine |
US9745860B1 (en) * | 2016-11-02 | 2017-08-29 | Jay HASKIN | Power transmission system for turbine or compressor having counter-rotating blades |
US10260367B2 (en) | 2016-11-02 | 2019-04-16 | Jay HASKIN | Power transmission system for turbines or compressors having counter-rotating blades |
US10392970B2 (en) * | 2016-11-02 | 2019-08-27 | General Electric Company | Rotor shaft architectures for a gas turbine engine and methods of assembly thereof |
US10190436B2 (en) * | 2016-11-02 | 2019-01-29 | Jay HASKIN | Power transmission system for turbine, a turbocharger, a compressor, or a pump |
US11053797B2 (en) | 2017-01-23 | 2021-07-06 | General Electric Company | Rotor thrust balanced turbine engine |
US10801442B2 (en) | 2017-02-08 | 2020-10-13 | General Electric Company | Counter rotating turbine with reversing reduction gear assembly |
US10823114B2 (en) | 2017-02-08 | 2020-11-03 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10465606B2 (en) | 2017-02-08 | 2019-11-05 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
GB201704502D0 (en) * | 2017-03-22 | 2017-05-03 | Rolls Royce Plc | Gas turbine engine |
US10294821B2 (en) * | 2017-04-12 | 2019-05-21 | General Electric Company | Interturbine frame for gas turbine engine |
CN106988882B (en) * | 2017-04-13 | 2019-03-01 | 深圳福世达动力科技有限公司 | Twin-stage is to turning gas turbine |
US10605168B2 (en) | 2017-05-25 | 2020-03-31 | General Electric Company | Interdigitated turbine engine air bearing cooling structure and method of thermal management |
US10669893B2 (en) | 2017-05-25 | 2020-06-02 | General Electric Company | Air bearing and thermal management nozzle arrangement for interdigitated turbine engine |
US10787931B2 (en) | 2017-05-25 | 2020-09-29 | General Electric Company | Method and structure of interdigitated turbine engine thermal management |
US10718265B2 (en) | 2017-05-25 | 2020-07-21 | General Electric Company | Interdigitated turbine engine air bearing and method of operation |
US10781717B2 (en) | 2017-09-20 | 2020-09-22 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10914194B2 (en) | 2017-09-20 | 2021-02-09 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10738617B2 (en) | 2017-09-20 | 2020-08-11 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US11098592B2 (en) | 2017-09-20 | 2021-08-24 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10823000B2 (en) | 2017-09-20 | 2020-11-03 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10508546B2 (en) | 2017-09-20 | 2019-12-17 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10458267B2 (en) * | 2017-09-20 | 2019-10-29 | General Electric Company | Seal assembly for counter rotating turbine assembly |
US10823001B2 (en) * | 2017-09-20 | 2020-11-03 | General Electric Company | Turbomachine with alternatingly spaced turbine rotor blades |
US10480322B2 (en) | 2018-01-12 | 2019-11-19 | General Electric Company | Turbine engine with annular cavity |
EP3578763A1 (en) | 2018-06-07 | 2019-12-11 | Haskin, Jay | Power transmission system for turbine, a turbocharger, a compressor, or a pump |
US11073088B2 (en) | 2019-02-20 | 2021-07-27 | General Electric Company | Gearbox mounting in a turbomachine |
US11085515B2 (en) | 2019-02-20 | 2021-08-10 | General Electric Company | Gearbox coupling in a turbomachine |
US11156097B2 (en) | 2019-02-20 | 2021-10-26 | General Electric Company | Turbomachine having an airflow management assembly |
US11021970B2 (en) | 2019-02-20 | 2021-06-01 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
US11753939B2 (en) | 2019-02-20 | 2023-09-12 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
US11118535B2 (en) | 2019-03-05 | 2021-09-14 | General Electric Company | Reversing gear assembly for a turbo machine |
FR3095670B1 (en) * | 2019-04-30 | 2021-12-03 | Safran Aircraft Engines | Improved architecture of a contra-rotating turbine engine |
GB201910009D0 (en) * | 2019-07-12 | 2019-08-28 | Rolls Royce Plc | Gas turbine engine electrical generator |
US11280219B2 (en) * | 2019-11-27 | 2022-03-22 | General Electric Company | Rotor support structures for rotating drum rotors of gas turbine engines |
US11274557B2 (en) * | 2019-11-27 | 2022-03-15 | General Electric Company | Damper assemblies for rotating drum rotors of gas turbine engines |
FR3111377B1 (en) * | 2020-06-10 | 2022-07-15 | Safran Aircraft Engines | Improved counter-rotating turbine turbomachine architecture |
US11512637B2 (en) | 2020-11-12 | 2022-11-29 | General Electric Company | Turbine engine bearing arrangement |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
US20240110504A1 (en) * | 2022-09-29 | 2024-04-04 | General Electric Company | Counter-rotating gas turbine engines including turbine sections with separable torque frames |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3861139A (en) * | 1973-02-12 | 1975-01-21 | Gen Electric | Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition |
US4950089A (en) * | 1988-05-12 | 1990-08-21 | Williams International Corporation | Compliant foil bearing |
US5307622A (en) * | 1993-08-02 | 1994-05-03 | General Electric Company | Counterrotating turbine support assembly |
US5450719A (en) | 1993-11-17 | 1995-09-19 | Alliedsignal, Inc. | Gas turbine engine rear magnetic or foil bearing cooling using exhaust eductor |
US5809772A (en) | 1996-03-29 | 1998-09-22 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct |
US5806303A (en) | 1996-03-29 | 1998-09-15 | General Electric Company | Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle |
US5867980A (en) | 1996-12-17 | 1999-02-09 | General Electric Company | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner |
US5813214A (en) | 1997-01-03 | 1998-09-29 | General Electric Company | Bearing lubrication configuration in a turbine engine |
FR2759734B1 (en) * | 1997-02-20 | 1999-04-09 | Snecma | TURBOMACHINE WITH OPTIMIZED COMPRESSION SYSTEM |
US6286303B1 (en) * | 1999-11-18 | 2001-09-11 | Allied Signal, Inc. | Impingement cooled foil bearings in a gas turbine engine |
US20020067872A1 (en) | 2000-12-01 | 2002-06-06 | Capstone Turbine Corporation | Hydrodynamic compliant foil thrust bearing |
US6725643B1 (en) | 2001-06-19 | 2004-04-27 | Marius Paul | High efficiency gas turbine power generator systems |
US6732502B2 (en) | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
US6619030B1 (en) * | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
US6739120B2 (en) | 2002-04-29 | 2004-05-25 | General Electric Company | Counterrotatable booster compressor assembly for a gas turbine engine |
US6684626B1 (en) | 2002-07-30 | 2004-02-03 | General Electric Company | Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines |
US6711887B2 (en) | 2002-08-19 | 2004-03-30 | General Electric Co. | Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines |
JP2004084877A (en) | 2002-08-28 | 2004-03-18 | Honda Motor Co Ltd | Foil bearing |
US6763653B2 (en) | 2002-09-24 | 2004-07-20 | General Electric Company | Counter rotating fan aircraft gas turbine engine with aft booster |
US6763652B2 (en) | 2002-09-24 | 2004-07-20 | General Electric Company | Variable torque split aircraft gas turbine engine counter rotating low pressure turbines |
US6763654B2 (en) | 2002-09-30 | 2004-07-20 | General Electric Co. | Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans |
-
2004
- 2004-10-29 US US10/976,496 patent/US7195446B2/en active Active
-
2005
- 2005-08-25 EP EP05255228A patent/EP1655475B1/en not_active Expired - Fee Related
- 2005-08-25 DE DE602005003759T patent/DE602005003759T2/en active Active
- 2005-08-26 JP JP2005245340A patent/JP4693551B2/en active Active
- 2005-08-29 CN CN200510097640XA patent/CN1854486B/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
CN1854486B (en) | 2011-08-24 |
US20060093466A1 (en) | 2006-05-04 |
DE602005003759T2 (en) | 2008-12-04 |
JP4693551B2 (en) | 2011-06-01 |
US7195446B2 (en) | 2007-03-27 |
EP1655475A1 (en) | 2006-05-10 |
DE602005003759D1 (en) | 2008-01-24 |
JP2006125387A (en) | 2006-05-18 |
CN1854486A (en) | 2006-11-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1655475B1 (en) | Counter-rotating turbine engine | |
EP1653045B1 (en) | Gas turbine engine | |
US7269938B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
US7334981B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
EP1316676B1 (en) | Aircraft engine with inter-turbine engine frame | |
CN107061008B (en) | Gas turbine engine | |
US7290386B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
US7186073B2 (en) | Counter-rotating gas turbine engine and method of assembling same | |
EP1655457B1 (en) | Gas turbine engine and method of assembling same | |
CA2524141C (en) | Counter-rotating turbine engine and method of assembling same | |
US6619030B1 (en) | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors | |
US10890247B2 (en) | Lubrication fluid collection in a gearbox of a gas turbine engine | |
EP2946131B1 (en) | Turbine engine | |
US10823083B2 (en) | Gearbox for a gas turbine engine | |
CA2948246A1 (en) | Modular fan for a gas turbine engine | |
US11225975B2 (en) | Gas turbine engine fan | |
CN108691568B (en) | Turbine interstage frame for a gas turbine engine | |
US20150361810A1 (en) | Fluid collection gutter for a geared turbine engine | |
US11414994B2 (en) | Blade retention features for turbomachines | |
US20230392555A1 (en) | Planetary gearbox device and gas turbine engine with a planetary gearbox device | |
CN113356929A (en) | Rotary support for interleaved rotor assemblies |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: GENERAL ELECTRIC COMPANY |
|
17P | Request for examination filed |
Effective date: 20061110 |
|
17Q | First examination report despatched |
Effective date: 20061208 |
|
AKX | Designation fees paid |
Designated state(s): DE FR GB IT |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB IT |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REF | Corresponds to: |
Ref document number: 602005003759 Country of ref document: DE Date of ref document: 20080124 Kind code of ref document: P |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20080915 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 12 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 13 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20200721 Year of fee payment: 16 Ref country code: DE Payment date: 20200721 Year of fee payment: 16 Ref country code: GB Payment date: 20200722 Year of fee payment: 16 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20200721 Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 602005003759 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20210825 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210825 Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210825 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20210831 Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220301 |